Abstract: A launcher is provided for a remotely piloted aircraft that has a launch ramp mounted on a transport vehicle and a carriage which is accelerated up the ramp carrying the aircraft to be launched. The carriage is hauled along the ramp by a cable leading to and wound around a winch drum which is driven by a flywheel through an electromagnetic slipping clutch, the flywheel being first run up to speed by an electric motor coupled to it by a torque limiting coupling. A hold-back device retains the carriage at the lower end of the ramp until the cable tension has built up to a predetermined value, and a brake system decelerates and arrests the carriage at the upper end as the aircraft leaves. On a short transport vehicle, the length of the ramp can be reduced for travel either by making it telescopic or by arranging it to fold about a hinge.

Abstract: An unmanned craft having a fuselage, a propeller drive with a propeller being arranged in the tail portion of the fuselage for purposes of cruising, and a rocket assist propulsion system for the takeoff phase is releasably mounted to the fuselage, the improvement includes three spring biased thrust rods being secured to the frame and releasably engaging peripheral points of the craft. The thrust rods are radially pivotal in outer direction. Support points on the wings and the rudder engage front ends of the rods in contourmatching relationship but are disengageable therefrom.

Abstract: A rapidly extendible, rough-field attenuating shock-absorbing strut, particularly adapted for use with an aircraft having a tricycle landing gear, is used during takeoff and is adapted for rapid extension to provide angular or upward momentum to the aircraft and thus facilitate takeoff. The strut comprises an outer cylinder which is secured to the aircraft and an inner cylinder adapted for longitudinal reciprocation within the outer cylinder. The inner cylinder has a wheel mounted thereon at the end opposite that of the outer cylinder. A piston is secured for longitudinal reciprocation within both the outer and inner cylinders. The piston has a piston head adapted for reciprocation within the outer cylinder.

Abstract: An extendable shock strut comprising a strut housing having an open end and a closed end and a piston including a piston housing and a piston head slidable in the strut housing. The piston housing and the strut housing are adapted to move a selected distance relative to one another under normal usage. A source of high pressure gas is provided coupled to the shock strut for rapidly driving the strut housing and the piston housing relative to one another to an extended position. In a particular embodiment of the invention, an expandable chamber is formed from the closed end of the strut housing and a secondary piston slidable in the strut housing and positioned between the closed end of the strut housing and the piston head. The high pressure gas rapidly expands the chamber and drives the secondary piston toward the piston head to cause the piston housing and the strut housing to move relative to one another to the extended position.

Abstract: A launching structure comprising a ram driven by a piston in a cylinder. A yrotechnic charge initiates a gas expansion underneath the piston and the expanding gases drive the ram. The ram has a helical groove engaged by a cam pin in the cylinder wall to impart a rotary motion to the ram as it is displaced linearly in the cylinder. A mass is engaged by the ram and is ejected from the cylinder with both a linear and rotational velocity.

Abstract: An aircraft of the hang glider type includes a wing (11) with a keel (12) in its plane of symmetry serving as a fastening point for a trapeze and a harness by which the pilot is suspended below the wing, the trapeze and the harness being disposed in conventional manner for suspending a pilot in the prone position. The invention provides a motor propeller unit (15) which is mounted in such a manner as to be movable at least in the longitudinal direction along the keel axis under pilot control, thereby enabling the pilot to displace both the center of gravity of the motor propeller unit and his own center of gravity between an extreme forward position ahead of the center of lift of the wing and an extreme rearward position behind the center of lift (1).

Abstract: A deceleration sled to decelerate and safely contain a launched test miss. The sled has crushable honeycomb which absorbs the initial impact of the missile as the sled accelerates along a track to the same speed as the missile. As the deceleration sled is pushed down the rails, forming shoes on both sides of the sled engage flat metal plates. The forming shoes roll the flat plates into a "U" shape. The energy required to roll these plates can be changed by varying their thickness.

Abstract: Lateral forces exerted on an air inflated, airfoil canopy of an aerial device during towline launching are balanced by slidable displacement of the coupling between the towline and a flexible guide attached at spaced locations to the aerial device. The flexible guide has a triangular configuration to control the distribution of towing force components and corresponding changes in orientation of the aerial device.

Abstract: A fluid pressure cylinder of the rodless type having a reciprocally movable piston, an elongated slot within the cylinder and an improved sealing element for successively sealing the elongated slot during movement of the piston. The improved sealing element is constructed of a generally flexible material and includes a sealing portion for creating a seal against the inner side wall of the cylinder adjacent to the elongated slot and a portion which is adapted for at least partial insertion wthin the slot so as to retain the seal member within the slot during an absence of pressure within the cylinder.

Abstract: A telescoping energy-dissipating oleo landing gear shock strut set which can provide both the main landing gear and forward landing gear function, and which is affixed to an airplane, is restrained in an unenergized, shortened condition. A high pressure gas charge is then provided between the extendible element of the strut and the element affixed to the airplane. Early in the takeoff run, the charge gas in the forward strut is released so as to jump the nose and rotate the airplane to a high angle of attack appropriate for takeoff. Subsequent to this rotation, but before the conventional takeoff speed is reached, the charge gas in each of the main struts is released to impart a vertical velocity to the entire airplane, thus jumping it into the air. Both the forward strut and main struts incorporate a hydraulic flow bypass function, so that the landing shock dissipation function does not compromise the aforesaid energy release.

Abstract: An unmanned aircraft vehicle to be launched from a container is provided with a rocket engine for launching and a propeller drive for cruising; the wings can be folded to the body of the vehicle and will be deployed as the vehicle leaves the launching container. The propeller is freely rotatable, even if the vehicle is still in the launching container. The rocket engine is releasably connected to at least one point on the propeller drive and in symmetrical relation to maintain the propeller drive coaxial to the propeller shaft, and to react rocket thrust directly into the propeller drive.

Abstract: This invention provides a system for launching aircraft into free flight regime regardless of runway conditions, wherein a sled of the self-powered air cushion vehicle type is configured in plan form so as to accept in temporarily locked relation thereupon and in combination therewith an airplane in such manner that a successful take-off run in mutually aerodynamically compatible regime may be accomplished in spite of surface problems with the runway. Upon attainment of airborne speed, under control of the pilot the aircraft lifts off the sled into full free flight; and thus is airborne albeit the runway is at the time unusable by conventional wheel-geared aircraft; for example, as the result of a previous bombing attack on the runway by enemy aircraft. The sled incorporates self-propelling and directional guidance means for retrieval/reuse purposes, as well as a take-off abort control system.

Abstract: A space shuttle system (11) having an orbiter spacecraft (16) with main rocket engines (43) a large external propellant tank (12), and two solid rocket boosters (13,14). The propellant tank (12) has a forward pressure vessel (19) for liquid hydrogen and an aft pressure vessel (20) for liquid oxygen. The two solid rocket boosters (13, 14) are joined together by a thrust frame (15) which extends behind the external tank. The thrust of the orbiter's main rocket engines (43) are transmitted to the aft portion of the external tank (12).

Abstract: A three stage rocket vehicle (11) having a large forward propellant tank (12) and a small aft propellant tank (13) axially aligned. Secured to the rear end of the aft propellant tank (13) is an engine mount structure (14) carrying rocket engines (15). Offset and secured to the propellant tanks (12,13) is a payload structure (18). The propellants from the large forward tank (12) are fed into the aft propellant tank (13) and the rocket engines (15) are fed propellants from the aft propellant tank (13). This arrangement enables the vehicle to parallel stage its use of engines and components.

Abstract: An aircraft take-off ramp, for causing an aircraft with a compressible, shock absorbing and damping landing gear to be so urged from a horizontal path that it follows an initially ballistic trajectory on leaving the ramp, has its profile derived from a notional generally circular arc. The notional arc has its radius selected so that the center of gravity of the aircraft, if its landing gear was incompressible, would follow a desired locus. The derived profile is so modified from the notional arc that during traverse of the ramp the compressible landing gear is compressed so that the center of gravity of the aircraft follows the desired locus.

Abstract: A flying craft which is pushed by a surface vehicle which follows the flying craft is disclosed. The craft includes a winged body which is connected by an elongated push pole to a ground engaging propelling vehicle. The control of the winged body is accomplished by changing the vertical position of one end of the elongated push pole relative to the opposite end of the flying craft. The surface vehicle limits the angle which the pole makes relative to the surface to prevent the surface vehicle from overtaking the flying craft.

Abstract: A vehicle or craft is provided for propeller propulsion with start assist by a releasable rocket engine. The craft is launched from a silo of square-shaped cross-section containing the starter motor for the propeller, whose engine is started while the craft is still in the silo. Diagonally opposed corners of the silo are provided with rails, in which run guides on rudder fins of the craft. The wings are pivoted to the fuselage for deployment whereby the wing tips do not move forward. The rocket engine is jettisoned shortly after take-off by simple disengagement. Parts of the wings and/or the rear of the fuselage may be jettisoned shortly before the craft reaches the target area.

Abstract: An aircraft undercarriage unit which includes an upper leg member 1 arranged for attachment to an aircraft body 4, a lower leg member 2 in axially slidable association with the upper leg member 1 to form a telescopic shock absorber, ground wheel means 6 carried by the lower leg member 2 and a sleeve member 13 through which the lower member extends and into which the upper leg member 1 may protrude. The sleeve member has anchorage means 17, 18 through which towing loads may be accepted and transmitted respectively.

Abstract: This invention relates to an improvement in a launch for carrying and launching flying bodies, in particular for aircraft, with guide devices in the form of guide rails and guide claws engaging said rails and bearing the flying body,the improvement comprising(a) means whereby the guide claws can be adjusted together with the flying body relative to the aircraft-fixed launch in the direction of flight within the guide rails and also relative to the flying body they carry in the direction of the flying body tail,(b) detachable, positive connection means and frictional connection means between the guide claws and the flying body, and(c) braking means for the guide claws at the launch.

Abstract: A ramp along which an aircraft having an undercarriage comprising two main units in tandem and two stabilizing units disposed one to each side of the main units travels during take-off, has a primary trackway (1) along which the wheels of the main undercarriage units roll, and secondary trackways (4, 5) along which the wheels of stabilizing units roll, the primary trackway alone having guides (14, 15) which maintain the wheels on the trackways, each trackway comprising a series of discrete members (19, 35) hinged one to the other in end-to-end relationship.

Abstract: A system for launching heavy rockets from the shaft of a launching tower where a cluster of liquid-propellant motors is mounted to its base and a series of clusters of solid-propellant motors are mounted in the tower's columns, the latter motors being consecutively upwardly fired. The rocket is supported by a piston impinged by the jet of gases ejected by the tower's motors. The impinging jet of gases spreads out of the shaft through open windows which are provided in the tower's walls and the rising movement of the rocket inside the shaft is controlled along a given path of movement in a manner that the firing of motors and closing of windows ensure controlled pressures below the piston and as a result, controlled accelerations. The rocket leaving the tower disconnects the impinging piston and then fires its own motors, having at that point a kinetic energy greater than usual.

Abstract: An aircraft carrier, the main deck of which is provided with an armored enclosure housing at least one work area for servicing aircraft. Service bays are arranged sequentially in the work area within the hangar in assembly-line fashion. Takeoff assisting means for the aircraft is provided on a portion of the main deck. The work areas can be divided by fire and explosion resistant doors which open and close with each refurbishing phase started or completed, with major increase in the speed of squadron operation.

Abstract: A fluid pressure actuated launching system for aircraft or other articles having a piston assembly with an exterior portion that engages the aircraft or article to be launched and an interior portion disposed within and adapted to move within a plurality of connected cylinders to provide a long working stroke and controlled acceleration of the piston and article to be launched. The cylinders are hinged to one another so that the launching system is collapsible to form a compact unit and facilitate portability and ready accommodation on a launch vehicle of limited size. The cylinders are provided with a longitudinal slot to permit passage of a web between the exterior and interior portions of the piston assembly. The slot is adapted to be sealed by a tensioned flexible closure ribbon that is operatively connected to the piston assembly and is restrained at both ends so that it does not travel.

Abstract: A portable "Ski-Jump" runway for use by Hawker Siddeley Harrier Type V/STOL aircraft and other conventional tricycle undercarriage aircraft having suitable performance characteristics. The runway comprises a main central ramp constructed on or as the chassis of a truck or trailer along which in use the main undercarriage wheels travel and secondary ramp sections of substantially lighter structural construction collapsibly mounted on support frames cantilevered from the main ramp section along which in use the secondary undercarriage wheels of the aircraft travel. The main ramp section is conveniently divided into at least two, preferably three, lengths, the foremost length being part of the truck or trailer and with the rearward length or lengths capable of being stored on top of the foremost length for transportation purposes. Component parts of the secondary ramp sections may be stored in the truck for transportation purposes.

Abstract: A launch platform for conventional landing gear aircraft having the launch platform configured as a ram wing structure with wheel latches secured to the platform. The platform is secured to the aircraft by means of the wheel latches. The wheel latches are released to permit the aircraft to leave the platform by pilot command. A parachute system is provided for platform deceleration after aircraft take-off. Spoilers are provided on the ram wing for stabilization of the ram wing during rotation.

Abstract: An orbit vehicle launch system including reusable turbojet propelled booster vehicles releasably connected to a reusable rocket powered orbit vehicle. The coupled orbiter-booster combination takes off horizontally and ascends to staging altitude and speed under booster power with both orbiter and booster wings providing lift. After staging, the booster vehicles fly back to earth for horizontal landing and the orbiter vehicle continues ascending to orbit.

Abstract: An improved dynamic seal for the longitudinal slot in a pressurized cylin of an aircraft catapult system having a shuttle adapted to travel at high speed through the slot. The seal includes a flexible, elongated sealing strip extended along the slot in sealing relation therewith to close the cylinder, and a series of ball detents mounted along the length of the slot on each side thereof for urging inwardly against the sides of the sealing strip thereby providing support for the strip throughout the length of the cylinder. When the shuttle, adapted to guide the strip internally of the cylinder as it passes therethrough, travels through the slot, the ball detents maintain the strip in sealing relation with the slot thereby preventing whipping of the strip forwardly of the moving shuttle.

Abstract: A pneumatic system for launching aircraft wherein an elongated frame having pressurized interior chamber is volumetrically related and communicatively connected to a longitudinally-slotted cylinder supported within the frame so that expansion of air into the cylinder produces a desired thrust pressure therein that is equalized by the residual pressure external of the cylinder within the chamber. A piston member slidably contained within the cylinder is adapted to receive the compressed air and is connected to a shuttle for accelerating the aircraft to be launched. The shuttle is releasably restrained at the rearward end of the cylinder and is adapted to travel longitudinally through the slot which is dynamically sealed by a flexible strip as the shuttle passes through the slot to preserve thrust pressure within the cylinder.

Abstract: A launching system for lightweight aircraft includes a shuttle adapted to rry the aircraft and slidingly mounted to a launching frame along a track that guides launch direction. A piston rod is concentrically mounted within a launch tube parallel to the track and is adapted to receive pneumatic pressure at the inward end thereof for driving the rod longitudinally outward of the tube during the launch stroke of the system. A crosshead having a pair of rotatable sheaves mounted thereon is rigidly connected to the outward end of the piston rod and slidingly connected to the track so that the crosshead moves along the track in conjunction with the longitudinal movement of the rod.

Abstract: An aircraft take-off runway, especially a ship's flight desk, is provided with a terminal ramp that curves upward to launch the aircraft in a semi-ballistic trajectory. The ramp is so configured as to have a varying contour or profile, in longitudinal section, at different regions across it, such that the path up the ramp of wheels on the center line of the aircraft is different from the path of wheels off the center line, e.g. outrigger wheels, whereby a desired pitching moment is imparted to the aircraft at launch.

Abstract: Kite launching apparatus including a control line with a portion thereof which is elastic. A portion of a Velcro holding structure is operatively attached to the kite or the control line. A stake is provided for being anchored to the ground. Another portion of the Velcro holding structure is operatively attached to the stake whereby the two portions of Velcro can be connected together. Once the Velcro holding structure portions are connected together the launching structure can be utilized by pulling on the control line to stretch the elastic portion thereof. When enough force has been applied to the Velcro holding structure to cause the two Velcro portions to come apart, the kite is automatically launched because of the pull of the elastic portion of the control line as it returns to its original shape.

Abstract: A toy kite has the general form of a hang glider and has a tow line which is releasable from the kite when in flight by slackening the tension in the tow line. Spars of the kite frame are hinged together by unitary plastic hinges and the frame can be folded and erected by moving a slider along a main spar. A pilot figure suspended in a harness below the kite is adjustable to alter the trim.

Abstract: Apparatus for restraining an aircraft against the combined forces of a cault launching shuttle and aircraft takeoff power during a catapult assisted takeoff until a predetermined combined force level has been reached. Release of the aircraft is triggered by the relative movement of a central piston within a housing which causes disengagement of gripping lugs from a tensile bar attached to the aircraft. The relative movement is enabled by the compressibility of hydraulic oil confined within the apparatus and loaded by the combined forces.

Abstract: A holdback bar for temporarily restraining an aircraft against the combined orces of engine thrust and catapult force prior to a catapult assisted launch of the aircraft which utilizes strain of a mechanical component to measure the level of combined forces. Housing stretch beyond a pre-determined amount actuates a floating trigger rod to lift a valve from its seat and permit escape of hydraulic fluid from a pressure chamber. The holdback bar includes a compensator for absorbing fluid volume changes caused by thermal expansion or contraction of the hydraulic fluid, and a rupture disk for limiting the pressure obtainable within the hydraulic fluid pressure chamber.

Abstract: A holdback bar for restraining an aircraft temporarily prior to catapult isted launch which utilizes a ball and piston unloader valve to insure rapid, positive release of a pressurized hydraulic fluid. Compensator chambers each having a resilient piston cushion against release shock caused by rapid release of stored strain energy in the hydraulic fluid and provide hydraulic fluid make-up to allow for expansion and contraction and slight leakage losses.

Abstract: The hydraulic energy absorbing device of U.S. Pat. Re. 28,736 is adapted to serve as a variable torque hydraulic clutch for a flywheel catapult by mobilizing the fixed array of annular vanes disposed about the rotor blades and mounting them on an output shaft. The torque transmission through the device is controlled by the degree of enclosure of the input rotor blade ring by a channel-shaped shroud, which is mounted in an annular recess in the toroidal flow-control ring disposed in an annular cavity in the casing.

Abstract: The shuttle for launching an RPV is connected to a launching tube by a motion and high speed-multiplying pulley and cable assembly. The telescopic launching tube assembly is connected between and parallel to a pair of elongated arms of a sealed U-shaped tubular assembly connected by a manifold to which the telescopic tube and shuttle are latched back against the force of compressed air stored in the U-shaped receiver. The release of the latch is damped to minimize acceleration forces on the launched RPV. The receiver and launching tubes are mounted on an elongated base whose rear end is rotatably connected to an anchor plate and the front end of the tubular assembly is adjustably mounted upon the front of the base on an adjustable jack support.

Abstract: A rocket-powered vehicle is held latched at the starting end of its guide track while a high steam pressure is built up within the rocket casings through probes inserted into the nozzles which also seal them. When the latch is released, the rockets move off the probes to unblock the nozzles whereby the rockets propel the vehicle down the track to launch the flying device.

Abstract: A method and apparatus for launching a remotely piloted aircraft is disclosed wherein the aircraft, is revolved about a fixed pivot point until a pretermined speed is reached whereupon the vehicle is released from the launching apparatus. The vehicle is attached to one end of a rotatable arm, the imbalance on the arm being counteracted by a counter weight attached to the opposite end. The counter weight is released from the arm at the same time as the aircraft so as to avoid structural damage to the apparatus caused by rotation in the unbalanced condition. The arm is oriented such that it rotates in a plane inclined obliquely to the local gravitational field of the launch site. The supporting structure for the arm may be made stationary, or may be attached to a mobile vehicle for ground transportation.

Abstract: A pneumatic launching apparatus for a lightweight aircraft has a battery of three pneumatic tubes mounted upon a hydraulic piston and cylinder assembly. A launching tube is mounted on the central pneumatic tube, which blows it away from it in a manner similar to that in which a tubular paper cover is blown off a drinking straw. The outer tubes provide additional storage for compressed air and support the outer ends of a launching carriage, which slides over them. The aircraft is mounted on the carriage by a pair of brackets which react against the aircraft in a forward-moving direction. Restraining shock absorbers are mounted across the front ends of the outer tubular rails in the path of movement of the carriage for arresting it. The pressure is exhausted from the system just before the carriage strikes the shock absorbers either by uncovering perforations in the central tubular rail or actuating a dump valve in the pneumatic system.

Abstract: An accelerator including a framework having an aerodynamic fairing shaped to provide positive pitch and directional stability and including a support and attachment system for holding a fully fueled horizontal takeoff space vehicle such that the negative structure loadings are reduced to a minimum. The running gear system includes a plurality of wheel tire sets with braking and decelerating systems associated therewith.